2024/05/14 更新

写真a

ワタナベ ヤスマサ
渡邉 保真
Yasumasa Watanabe
所属
大学院工学研究科 機械システム分野 流体工学研究室 准教授   
学位
博士(工学) ( 東京大学 )
外部リンク
連絡先
メールアドレス

研究分野

  • フロンティア(航空・船舶) / 航空宇宙工学

  • ものづくり技術(機械・電気電子・化学工学) / 流体工学

主な研究論文

経歴

  • 豊田工業大学   工学部   准教授

    2022年4月 - 現在

  • University of Notre Dame   Institute for Flow Physics and Control, Department of Aerospace and Mechanical Engineering   Guest Assistant Professor

    2018年4月 - 2020年3月

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    国名:アメリカ合衆国

  • 独立行政法人日本学術振興会   海外特別研究員

    2018年4月 - 2020年3月

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    国名:日本国

  • University of Notre Dame   Institute for Flow Physics and Control, Department of Aerospace and Mechanical Engineering   Guest Assistant Professor

    2017年2月 - 2017年4月

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    国名:アメリカ合衆国

  • 東京大学   大学院工学系研究科 航空宇宙工学専攻   助教

    2014年4月 - 2022年3月

  • 独立行政法人日本学術振興会   特別研究員(DC1)

    2011年4月 - 2014年3月

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    国名:日本国

▼全件表示

学歴

  • 東京大学   大学院工学系研究科   航空宇宙工学専攻

    2009年4月 - 2014年3月

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    国名: 日本国

  • 東京大学   工学系研究科   航空宇宙工学専攻

    2009年4月 - 2014年3月

  • 東京大学   工学部   航空宇宙工学科

    2005年4月 - 2009年3月

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    国名: 日本国

所属学協会

  • アメリカ物理学会

    2018年 - 現在

  • 日本航空宇宙学会

    2009年 - 現在

  • 米国航空宇宙学会

    2009年 - 現在

委員歴

  • 日本衝撃波研究会   幹事  

    2024年4月 - 現在   

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    団体区分:学協会

  • 日本航空宇宙学会   空気力学部門幹事  

    2021年4月 - 2023年3月   

  • 日本航空宇宙学会   空気力学部門委員  

    2020年4月 - 2021年3月   

  • 日本航空宇宙学会   空気力学部門委員  

    2016年4月 - 2018年3月   

▼全件表示

研究テーマ

  • 流線壁を有するスクラムジェットエンジンによる燃焼効率向上に関する研究

    渡邉 保真

    2023年度 - 現在

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    超音速輸送機に用いられるスクラムジェットエンジンにおける,水素燃料混合促進と全圧損失低減を目指す.

    成果:

    2023年度
    内部流れの最適化を目指し,流線型壁を有するスクラムジェットエンジン燃焼室での水素燃料混合と全圧損失を,複数化学種に対するNavier-Stokes方程式及びSST乱流モデルにより解析し,全圧損失を抑えつつも,従来型エンジンよりも大きく水素混合を行うことが可能な形状が存在することが判明した.

  • 宇宙機用全固体推進器の研究開発

    渡邉 保真

    2023年度 - 現在

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    小型宇宙機への搭載を目指し,液体・気体燃料を使用しない推進器の研究開発を行う

    成果:

    2023年度
    小型宇宙機の推進器として用いるべく,全固体イオンエンジンの基礎研究を開始し,動作条件と推力の推算等を行った.

  • 将来型高速旅客機周りでの水の相変化を伴う流れの影響に関する研究

    渡邉 保真

    2017年度 - 現在

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    将来型高速航空機における着氷現象に関する基礎研究を行う

    成果:

    2023年度
    極超音速気流中での着氷現象解析モデルを作成するため,マッハ数7での極超音速風洞実験を実施し,実験的に得られた水滴・水蒸気分布と,簡易予測モデルにより得られた結果を比較検証した.

    2022年度
    高速気流中での水の相変化と着氷に関する現象について,風洞実験による計測を行い,それに対応する簡易モデルを作成した.

  • 火山噴火や将来型超音速旅客機に伴う衝撃波の建造物に対する影響低減に関する研究

    渡邉 保真

    2017年度 - 現在

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    火山噴火や航空機運航に伴って発生した衝撃波による建造物への影響を低減するための構造物の提案とその性能評価を行う.

    成果:

    2023年度
    角柱を用いた衝撃波減衰構造を提案し,それによる衝撃波減衰効果について,感圧塗料による高速圧力計測と,3次元Navier-Stokes方程式に基づく数値解析を実施し,減衰効果の有効性を検証した.

    2022年度
    簡易的な衝撃波減衰構造を提案し,それによる衝撃波減衰効果について,感圧塗料による実験的計測と数値解析を実施した.

  • 放電プラズマを用いた極超音速気流制御に関する研究

    渡邉 保真

    2017年度 - 現在

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    放電プラズマを利用した高速気流制御と,これを利用した航空機の空力制御性能を明らかにする.

    成果:

    2023年度
    極超音速機外部ノズル部における高速気流制御効果について,極超音速風洞実験による圧力計測に基づく検証と,それに対応する数値解析を通して効果的な制御効果について調査した.

    2022年度
    放電プラズマによる極超音速気流制御効果について,極超音速風洞実験による定量的評価と,それに対応する数値解析を通して効果的な制御効果について調査した.

論文

  • タイルギャップを模擬した極超音速平板流れに対する 噴き出し冷却法に関する研究 査読

    古谷元和, 渡邉 保真, 鈴木 宏二郎

    日本航空宇宙学会論文集   71 ( 3 )   112 - 120   2023年5月

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    掲載種別:研究論文(学術雑誌)  

    DOI: 10.2322/jjsass.71.112

  • Ultrasonic-driven synthetic-jet actuator: High-efficiency actuator creating high-speed and high-frequency pulsed jet 査読

    Satoshi Yuura*, Yasumasa Watanabe, Katsushi Furutani, Taro Handa

    Sensors and Actuators A: Physical   353   114231   2023年2月

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    掲載種別:研究論文(学術雑誌)   出版者・発行元:Elsevier  

  • Experimental and Numerical Study of Hypersonic Flow over Backward-Facing Step 査読

    ZHONG Ce, SUZUKI Kojiro, WATANABE Yasumasa

    TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN   19 ( 5 )   735 - 743   2021年 (     eISSN:1884-0485 )

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    記述言語:英語   掲載種別:研究論文(学術雑誌)   出版者・発行元:THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES  

    Experimental and numerical studies were conducted to investigate the flow over a backward-facing step with finite aspect ratio. Measurements using pressure-sensitive paint, infrared thermal imaging, oil-flow visualization and schlieren imaging were conducted in the Hypersonic and High Enthalpy Wind Tunnel at the University of Tokyo. The results show the complex three-dimensional structure of the flow over a backward-facing step. The numerical simulation was also conducted, and the simulation results reveal that the fluid flow from the open side of the model has significant three-dimensional effect on the flow features. Comparison between CFD and experimental results is also made in this paper. A recirculation bubble found after the step, generated by the interaction of side expansion and recirculating flow, is observed in CFD results. A symmetric local peak pressure and heating region named ‘twin peak’ is also founded by both numerical simulation and experiments.

    DOI: 10.2322/tastj.19.735

  • Flow-field and performance study of coaxial supersonic nozzles operating in hypersonic environment 査読

    Mohammad Samara, Ashish Vashishtha, Yasumasa Watanabe, Kojiro Suzuki

    International Review of Aerospace Engineering   13 ( 1 )   25 - 39   2020年 (   ISSN:1973-7459   eISSN:2533-2279 )

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    掲載種別:研究論文(学術雑誌)  

    © 2020 Praise Worthy Prize S.r.l.-All rights reserved. The integration of multiple propulsion systems in a coaxial configuration is one of the challenges to realize hypersonic passenger transportation. This study is an attempt to understand the performance of two co-axial jets exiting from the base of slender body, operating in single and dual operation mode in freestream hypersonic flow environment. In addition, the effects on performance by adding a different length common channel to both co-axial jets are studied. In the first part of this study, the experiments have been performed for small slender body kept in hypersonic Mach 7 flow, which consists of two inner high-pressure chambers and two co-axial nozzles at the base: central nozzle (Mach 4) and surrounding nozzle (Mach 2.8) along with extended common region, termed as common channel. Schlieren images have been captured for single and dual operation modes. Axisymmetric numerical simulations have been performed for further understanding of the flow interactions and have been qualitatively validated with experimental images. In the second part, the parametric study has been performed using numerical simulations for resized model with various exit Mach numbers for central and surrounding jets along with effect of no common channel and with common channel for various operation modes. One of the findings of the study is that dual jets should operate and exit at same plane (no common channel) with the same exit area (each nozzle with half of total available exit area) in order to have higher total thrust from both jets than the sum of individual jets operating in single operation mode. For higher central jet Mach numbers, the corresponding surrounding jet Mach number will be lower, and in dual operation mode (without common channel), the total thrust will be the same or lower than the sum of the individual jet operations. Regarding the effect of common channel, it has been found out that the introduction of the extended short or long common channel in dual mode operation does not have significant effect on thrust, while the jet flow field is strongly affected by the common channel presence. In single operation mode, for Mach 2 central-jet, the thrust performance decreases 12.2-14.6 % in presence of short and long (29.5 mm and 59 mm) common channel, while for Mach 2 surrounding jet, the thrust performance increases by 15-17.4 % in presence of common channel.

    DOI: 10.15866/irease.v13i1.18282

  • Rapid control of force/momentum on a model ramp by quasi-DC plasma 査読

    Yasumasa Watanabe, Skye Elliott, Alexander Firsov, Alec Houpt, Sergey Leonov

    Journal of Physics D: Applied Physics   52 ( 44 )   2019年8月 (   ISSN:0022-3727   eISSN:1361-6463 )

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    担当区分:筆頭著者, 責任著者   記述言語:英語   掲載種別:研究論文(学術雑誌)   出版者・発行元:IOP PUBLISHING LTD  

    © 2019 IOP Publishing Ltd. The results of experimental and computational studies are considered on a near surface electric discharge effect on supersonic airflow near a 15° compression surface. The tests were performed at Mach number M = 2, stagnation pressure P 0 = 1-2.8 bar, stagnation temperature T 0 = 290-600 K, and plasma power W pl = 6-12 kW. They demonstrated a significant effect of plasma on the flow structure and reduction of static pressure on the compression surface. Transient phenomena were analyzed and it was found that the pressure decrease on the ramp was as fast as t < 0.3 ms. Simulations based on 3D unsteady Navier-Stokes equations with plasma modeled as an array of lengthwise heat sources demonstrated adequacy of such simplifications. Further simulations attempted to find an optimal range of plasma power and position in terms of achievable effect, effectiveness of the method, and response time of the system to the plasma actuation. The electric discharge authority for a fast and effective control of aerodynamic forces in a compression ramp configuration is considered.

    DOI: 10.1088/1361-6463/ab352f

  • Total thrust control method with propeller and electrically driven wheel for electric aircraft 査読

    Toshiki Niinomi, Hiroshi Fujimoto, Yasumasa Watanabe, Akira Nishizawa, Hiroshi Kobayashi

    Proceedings - 2018 IEEE 15th International Workshop on Advanced Motion Control, AMC 2018   281 - 286   2018年6月

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    掲載種別:研究論文(国際会議プロシーディングス)  

    © 2018 IEEE. Demand for aircraft transportation has doubled in the past ten years and is expected to increase. On the other hand, electrification of the aircraft's equipment is gradually improving. As part of this electrification, mounting of electrically driven wheel is considered. Our previous research also proposed safety landing by electrically driven wheel. In this paper, we propose the total thrust control method using propeller and electrically driven wheel in ground run. This method can accelerate in constant value on dry or wet road surface. We demonstrate the effectiveness of the proposed method by simulations and basic experiments.

    DOI: 10.1109/AMC.2019.8371103

  • Effect of Opposing Multiphase Jet on Hypersonic Flow Around Blunt Body 査読

    Zhong Ce, Rei Tomita, Kojiro Suzuki, Yasumasa Watanabe

    IOP Conference Series: Materials Science and Engineering   249 ( 1 )   2017年10月 (   ISSN:1757-8981   eISSN:1757-899X )

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    記述言語:英語   掲載種別:研究論文(国際会議プロシーディングス)   出版者・発行元:IOP PUBLISHING LTD  

    © 2017 Published under licence by IOP Publishing Ltd. An experimental research has been conducted to investigate the flow control method using opposing jet with air and water as a fluid spike on a bunt body in hypersonic freestream at Mach number 7, using the Kashiwa hypersonic wind tunnel. The dynamic characteristics and instability of opposing jet were clarified. It can be seen from the comparison between the air opposing jet and the water opposing jet that a liquid jet seems more effective in generating fluid spike for reduction in the drag force and the heating rate on the body. Details of the flow field and the jet oscillation have been captured by Schlieren system with high-speed cameras. The experimental data reveal the interaction of the jet oscillation with the shock wave fluctuation. Such interaction has strong impact on the whole flow field structure and should be taken into consideration in the design of the active flow control system using the opposing jet method.

    DOI: 10.1088/1757-899X/249/1/012014

  • Plasma-Assisted Control of Mach-2 Flowfield over Ramp Geometry 査読

    Yasumasa Watanabe, Sergey B. Leonov, Alec Houpt, Brock E. Hedlund, Skye Elliott

    IOP Conference Series: Materials Science and Engineering   249 ( 1 )   2017年10月 (   ISSN:1757-8981   eISSN:1757-899X )

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    担当区分:筆頭著者, 責任著者   記述言語:英語   掲載種別:研究論文(国際会議プロシーディングス)   出版者・発行元:IOP PUBLISHING LTD  

    © 2017 Published under licence by IOP Publishing Ltd. This study examined the effect of Reynolds number on plasma-assisted flow control ahead of a compression ramp geometry in Mach-2 supersonic flow. The experiments were conducted in the supersonic wind tunnel SBR-50 at the University of Notre Dame. Stagnation temperature and pressure were varied as T0=294-500K and P0=1-3bar to attain Reynolds number ranging from 3.4×105-2.2×106. Ramp pressure measurements, schlieren visualization, and high-speed camera imaging were used for the evaluation of plasma-assisted flow control effects. A linear dependency was found between the ramp pressure change per averaged plasma power and Reynolds number.

    DOI: 10.1088/1757-899X/249/1/012006

  • Visualization of Projectile Flying at High Speed in Dusty Atmosphere 査読

    Chihiro Masaki, Yasumasa Watanabe, Kojiro Suzuki

    IOP Conference Series: Materials Science and Engineering   249 ( 1 )   2017年10月 (   ISSN:1757-8981   eISSN:1757-899X )

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    記述言語:英語   掲載種別:研究論文(国際会議プロシーディングス)   出版者・発行元:IOP PUBLISHING LTD  

    © 2017 Published under licence by IOP Publishing Ltd. Considering a spacecraft that encounters particle-laden environment, such as dust particles flying up over the regolith by the jet of the landing thruster, high-speed flight of a projectile in such environment was experimentally simulated by using the ballistic range. At high-speed collision of particles on the projectile surface, they may be reflected with cracking into smaller pieces. On the other hand, the projectile surface will be damaged by the collision. To obtain the fundamental characteristics of such complicated phenomena, a projectile was launched at the velocity up to 400 m/s and the collective behaviour of particles around projectile was observed by the high-speed camera. To eliminate the effect of the gas-particle interaction and to focus on only the effect of the interaction between the particles and the projectile's surface, the test chamber pressure was evacuated down to 30 Pa. The particles about 400μm diameter were scattered and formed a sheet of particles in the test chamber by using two-dimensional funnel with a narrow slit. The projectile was launched into the particle sheet in the tangential direction, and the high-speed camera captured both projectile and particle motions. From the movie, the interaction between the projectile and particle sheet was clarified.

    DOI: 10.1088/1757-899X/249/1/012015

  • Aerodynamic characteristics of breathing blunt nose configuration at hypersonic speeds 査読

    Yasumasa Watanabe, Kojiro Suzuki, Ethirajan Rathakrishnan

    Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering   231 ( 5 )   840 - 858   2017年4月 (   ISSN:0954-4100   eISSN:2041-3025 )

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    担当区分:筆頭著者   記述言語:英語   掲載種別:研究論文(学術雑誌)  

    © IMechE 2016. Breathing blunt nose technique is one of the promising methods for reducing the drag of blunt-nosed body at hypersonic speeds. The air, traversed by the bow shock positioned ahead of the nose, at the stagnation region is allowed to enter through a hole at the blunt-nose and ejected at the rear part (base region) of the body. This manipulation reduces the positive pressure over the stagnation regions of the nose and increases the pressure at the base, resulting in reduced suction at the base. The simultaneous manifestation of reducing the compression at the nose and suction at the base regions results in reduction of the total drag. The drag reduction caused by the breathing blunt nose technique has been measured in a Mach 7 tunnel. Also, the drag and flow field around the blunt-nosed body, with and without breathing hole, has been computed. The aerodynamic characteristics of the breathing blunt nose model obtained experimentally are compared with the CFD results. It is found that the breathing results in 5% reduction in drag. The lift coefficient also comes down for the model with breathing nose. But the lift-to-drag ratio is found to be the same for both the cases; the blunt-nosed body with and without nose-hole.

    DOI: 10.1177/0954410016643979

  • Performance prediction of electrohydrodynamic thrusters by the perturbation method 査読

    H. Shibata, Y. Watanabe, K. Suzuki

    Physics of Plasmas   23 ( 5 )   2016年5月 (   ISSN:1070-664X   eISSN:1089-7674 )

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    掲載種別:研究論文(学術雑誌)  

    © 2016 Author(s). In this paper, we present a novel method for analyzing electrohydrodynamic (EHD) thrusters. The method is based on a perturbation technique applied to a set of drift-diffusion equations, similar to the one introduced in our previous study on estimating breakdown voltage. The thrust-to-current ratio is generalized to represent the performance of EHD thrusters. We have compared the thrust-to-current ratio obtained theoretically with that obtained from the proposed method under atmospheric air conditions, and we have obtained good quantitative agreement. Also, we have conducted a numerical simulation in more complex thruster geometries, such as the dual-stage thruster developed by Masuyama and Barrett [Proc. R. Soc. A 469, 20120623 (2013)]. We quantitatively clarify the fact that if the magnitude of a third electrode voltage is low, the effective gap distance shortens, whereas if the magnitude of the third electrode voltage is sufficiently high, the effective gap distance lengthens.

    DOI: 10.1063/1.4951721

  • Attitude Estimation of Nano-satellite with Deployable Aeroshell during Orbital Decay 査読

    WATANABE Yasumasa, SUZUKI Kojiro, IMAMURA Osamu, YAMADA Kazuhiko

    TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN   14 ( 30 )   Pf_1 - Pf_5   2016年 (   ISSN:1884-0485 )

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    担当区分:筆頭著者, 責任著者   記述言語:英語   掲載種別:研究論文(学術雑誌)   出版者・発行元:一般社団法人 日本航空宇宙学会  

    As a part of the "Membrane Aeroshell for Atmospheric-entry Capsule" (MAAC) project pursued by the University of Tokyo, JAXA and several other universities, a demonstration is planned to deploy an atmospheric-entry nano-satellite from International Space Station (ISS). The effect of aeroshell deployment timing on the orbital decay was evaluated and it was clarified that the orbital decay is significantly accelerated after aeroshell deployment due to the change in its ballistic coefficient. In order to keep the forward surface of the aeroshell in the direction of motion at the moment of aeroshell deployment, it is necessary to obtain the attitude of satellite with reference to the orbital direction. The applicability of the Faraday cup as an ion detector is discussed through experimental results at Inductively Coupled Plasma (ICP) wind tunnel and it was revealed to be promising for the estimation of the satellite direction.<b> </b>

    DOI: 10.2322/tastj.14.Pf_1

  • Study on Dynamics of Penetrator into Ice 査読

    SUZUKI Kojiro, NAMBA Kazuya, WATANABE Yasumasa

    TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN   14 ( 30 )   Pk_65 - Pk_71   2016年

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    記述言語:英語   掲載種別:研究論文(学術雑誌)   出版者・発行元:一般社団法人 日本航空宇宙学会  

    <p>To realize the penetrator mission for icy objects in the solar system, the penetration dynamics into ice has been experimentally and numerically studied. In the experiments, the ogive/cylinder projectiles of the mass about 2.6 g were tested for the target made from water ice by the ballistic range at the impact velocity 100-350 m/s. The behavior of the projectile and target was observed by the high-speed video camera. The penetration trajectory was visualized by pouring the plaster into the crater. The empirical analysis model to describe the force acting on the body surface has been developed, based on the panel method and the shock wave analogy. It includes two parameters representing the effective speed of sound of crushed ice and the damping of the pitching motion. Fairly good agreement with the experiments was obtained with respect to the stop conditions of the penetrator by setting these parameters appropriately. The computational result assuming a flight model of the mass 14.9 kg and the impact velocity 300 m/s shows that the maximum deceleration G is in the same order as that for the lunar penetrator.</p>

    DOI: 10.2322/tastj.14.Pk_65

  • Global stability analysis method to numerically predict precursor of breakdown voltage 査読

    Hisaichi Shibata, Yuya Ohmichi, Yasumasa Watanabe, Kojiro Suzuki

    Plasma Sources Science and Technology   24 ( 5 )   2015年9月 (   ISSN:0963-0252   eISSN:1361-6595 )

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    記述言語:英語   掲載種別:研究論文(学術雑誌)   出版者・発行元:IOP PUBLISHING LTD  

    � 2015 IOP Publishing Ltd. This study presents a new method for predicting a precursor of breakdown voltage. This method applies a global linear stability analysis to a drift-diffusion model coupled with the Poisson equation. The instability of the solution of these equations is evaluated with the proposed method and is considered to be the onset of a breakdown. The proposed method is validated in one dimension by using the Townsend theory as a reference. To extend the one-dimensional case and investigate the characteristics of multidimensional eigenmodes, we apply the method to two-dimensional plane-to-plane discharge tubes. To prove an adaptability against complex electrodes geometry, the discharge path and the corresponding breakdown voltage for the well-known corner-to-plane geometry are qualitatively evaluated.

    DOI: 10.1088/0963-0252/24/5/055014

  • Lift control of electric airplanes by using propeller slipstream for safe landing 査読

    Nobukatsu Konishi, Hiroshi Fujimoto, Yasumasa Watanabe, Kojiro Suzuki, Hiroshi Kobayashi, Akira Nishizawa

    Proceedings - 2015 IEEE International Conference on Mechatronics, ICM 2015   335 - 340   2015年4月

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    掲載種別:研究論文(国際会議プロシーディングス)  

    © 2015 IEEE. Aircrafts are desired to be more energy efficient and safer due to the increasing demand for air transportations. However, generally speaking, nowadays commercial airplanes tend to loss stability under wind disturbances, especially during landing. On the other hand, electric airplanes (EAs) are believed to satisfy the two demands because electric motors are used for the propulsion. Especially, as the actuators, electric motors can improve the control performances of EAs compared with internal combustion engines (ICEs). In this paper, by utilizing electric motors' advantages, lift control method using propeller slipstream is proposed for safe landing, which might be a key technology to innovate the design of EAs. Moreover, simulations and experiments are conducted to verify the effectiveness of the proposed method.

    DOI: 10.1109/ICMECH.2015.7083998

  • Effectiveness of Direct Current Arc Plasma Discharge on Aerodynamic Control in Hypersonic Flow 査読

    WATANABE Yasumasa, SUZUKI Kojiro

    TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN   12 ( 29 )   Pe_1 - Pe_4   2014年 (   ISSN:1884-0485 )

     詳細

    担当区分:筆頭著者, 責任著者   記述言語:英語   掲載種別:研究論文(学術雑誌)   出版者・発行元:THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES  

    In this study, the application of direct current arc plasma discharge is discussed through computational analysis on the flow around a bump-up shape over a surface of a typical hypersonic vehicle under 20-km altitude and Mach-5 flight condition. Numerical simulation based on our simple plasma model suggested that the front pressure over a bump-up slope could be decreased by the use of plasma actuation method proposed in this study. The plasma source generated at 7 cm ahead of the bump successfully reduced the drag coefficient for more than 56%, changing the surface flow to go smoothly along the surface of the bump shape.

    DOI: 10.2322/tastj.12.Pe_1

  • Numerical Study on Fundamental Characteristics of Electro-Hydrodynamic Thruster for Mobility in Planetary Atmosphere 査読

    SHIBATA Hisaichi, WATANABE Yasumasa, YANO Ryosuke, SUZUKI Kojiro

    TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN   12 ( 29 )   Pe_5 - Pe_9   2014年 (   ISSN:1884-0485 )

     詳細

    記述言語:英語   掲載種別:研究論文(学術雑誌)   出版者・発行元:THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES  

    The EHD (electro-hydrodynamic) thruster seems suitable for a device of mobility at planetary exploration because of its propellant-less nature. In this paper, the fundamental characteristics of the EHD thruster are investigated from a viewpoint of the applicability to the planetary exploration. The numerical analysis of the drift-diffusion equations shows that it works irrespective to the polarity of the electrodes because the polarity of the produced ions is also changed. This fact implies that it will work in different atmospheric composition with different polarity of the produced ions. It is also numerically found that the thrust tends to increase with the decrease in the ambient pressure. For simplicity of discussion, a simple analytical model to describe the energy conversion efficiency is derived, and it indicates that higher efficiency is expected in higher Knudsen number regime. Both the above results suggest that the EHD thruster is promising especially in planetary atmosphere with low density.

    DOI: 10.2322/tastj.12.Pe_5

  • Effect of Rarefied Gas Dynamics on Response of Air Data Sensor System for Atmospheric Entry Vehicle Flying at High Altitudes 査読

    WATANABE Yasumasa, YANO Ryosuke, HONMA Naohiko, NAGATA Yasunori, YAMADA Kazuhiko, SUZUKI Kojiro

    Trans Jpn Soc Aeronaut Space Sci Aerosp Technol Jpn (Web)   12 ( ists29 )   TO.2.1-TO.2.5 (J-STAGE)   2014年 (   ISSN:1884-0485 )

     詳細

    担当区分:筆頭著者, 責任著者   記述言語:英語   掲載種別:研究論文(学術雑誌)  

    DOI: 10.2322/tastj.12.To_2_1

  • Pressure hill and zone of influence over flat-faced bluff bodies 査読

    Yasumasa Watanabe, Kojiro Suzuki, Ethirajan Rathakrishnan

    International Journal of Turbo and Jet Engines   28 ( 4 )   329 - 333   2011年12月 (   ISSN:0334-0082   eISSN:2191-0332 )

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    担当区分:筆頭著者, 責任著者   記述言語:英語   掲載種別:研究論文(学術雑誌)   出版者・発行元:WALTER DE GRUYTER & CO  

    An experimental visualization has been carried out to study the dependence of the pressure hill height and the influence zone expanse for flow past rectangular blocks of flat square face and varying length, over a Reynolds number range from 1364 to 4931. It is found that, the pressure hill length and the influence zone expanse decrease with the length to width ratio of the block, up to about L/W 1, for Reynolds number up to 1586. For higher Reynolds numbers, both H/W and Z/W increase with the model length, till L/W 1. For L/W more than 1, both H/W and Z/W gradually become independent of L/W. The ratio of Z/H is influenced only marginally by L/W up to 1, and for greater values of L/W, Z/H is almost a constant at all Reynolds numbers of the present study. Copyright © 2011 De Gruyter.

    DOI: 10.1515/TJJ.2011.067

  • Visualization of Processes Caused by Direct Current Plasma Discharge in Hypersonic Flow Over Flat Plate 査読

    Y Watanabe, K Suzuki

    Visualization of Mechanical Processes   1 ( 3 )   2011年

     詳細

    担当区分:筆頭著者, 責任著者   記述言語:英語   掲載種別:研究論文(学術雑誌)  

    DOI: 10.1615/VisMechProc.v1.i3.50

  • Preliminary Studies on Aerodynamic Control with Direct Current Discharge at Hypersonic Speed 査読

    WATANABE Yasumasa, TAKAMA Yoshiki, IMAMURA Osamu, WATANUKI Tadaharu, SUZUKI Kojiro

    TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN   8 ( 27 )   Pe_15 - Pe_20   2010年 (   ISSN:1884-0485 )

     詳細

    担当区分:筆頭著者, 責任著者   記述言語:英語   掲載種別:研究論文(学術雑誌)   出版者・発行元:THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES  

    A new idea of an aerodynamic control device for hypersonic vehicles using plasma discharges is presented. The effect of DC plasma discharge on a hypersonic flow is examined with both experiments and CFD analyses. It is revealed that the surface pressure upstream of plasma area significantly increases, which would be preferable in realizing a new aerodynamic control devices. Such pressure rise is also observed in the result of analyses of the Navier-Stokes equations with energy addition that simulates the Joule heating of a plasma discharge. It is revealed that the pressure rise due to the existence of the plasma discharge can be qualitatively explained as an effect of Joule heating.

    DOI: 10.2322/tastj.8.Pe_15

▼全件表示

MISC

  • 第54回流体力学講演会/第40回航空宇宙数値シミュレーション技術シンポジウム開催報告 査読

    渡邉 保真

    日本航空宇宙学会誌   70 ( 12 )   263 - 264   2022年12月

     詳細

    担当区分:筆頭著者   掲載種別:記事・総説・解説・論説等(その他)   出版者・発行元:日本航空宇宙学会  

  • Q-dc plasma actuation for mach-4 supersonic flow control over compression ramp

    Yasumasa Watanabe, Skye Elliott, Alec Houpt, Sergey B. Leonov

    AIAA Scitech 2020 Forum   1 PartF   2020年

     詳細

    担当区分:筆頭著者  

    © 2020, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved. In this study, a quasi direct-current (Q-DC) filamentary plasma was employed for control of Mach-4 supersonic flow over a compression ramp. A 15-degree ramp model was placed on a test section wall at the SBR-50 facility. An array of 5 electrodes were installed 30 mm upstream of the ramp to attain rapid flow control. Schlieren visualization was performed with a high-speed camera to clarify the details and dynamics of plasma-flow interaction. Kulite™ pressure transducers were placed over the test model to measure the fast pressure disturbances. The data on pressure dynamics at the ramp was analyzed to evaluate the plasma actuation effectiveness. The flowfield structure and shock wave positions were significantly modified due to the Q-DC plasma actuation. The pressure on the ramp was reduced during the plasma pulse and the reduction was nearly a linear function of plasma power. It was also found that the pitching moment coefficient around the leading edge of the ramp is a linear function of a relative plasma power, suggesting a linear control of aerodynamic moments at practical application.

    DOI: 10.2514/6.2020-1889

  • Plasma-based control of mach-2 supersonic flow over compression ramp

    Yasumasa Watanabe, Sergey B. Leonov, Alec Houpt

    AIAA Scitech 2019 Forum   6 ( 3 )   2019年 (   ISSN:2226-4310   eISSN:2226-4310 )

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    担当区分:筆頭著者   記述言語:英語   出版者・発行元:MDPI  

    © 2019, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved. This study examined the control effect of Q-DC electric discharge on the surface pressure of a 12-degree compression ramp in Mach-2 supersonic flow. The experiments were conducted in the supersonic wind tunnel SBR-50 at the University of Notre Dame. Stagnation pressure and temperature were varied as P0=1-3bar and T0=300-600K respectively to attain various flow conditions. Ramp pressure measurements, schlieren visualization, and high-speed camera imaging were used for evaluation of plasma control effects. Plasma voltage spectra based on FFT analysis indicated that there are multiple characteristic frequencies, which are correlated with repetitive plasma motion through dynamic mode decomposition analysis and categorized into streamwise-and transverse-oscillation modes. Ramp pressure variation was found to be a linear increasing function of average plasma power and plasma power to flow enthalpy flux ratio.

    DOI: 10.2514/6.2019-1348

  • 極超音速機フラップ前方での放電及び磁場による空力制御に関する研究

    渡邉 保真, 鈴木 宏二郎

    宇宙科学技術連合講演会講演集   60   5p   2016年9月 (   ISSN:1884-1945 )

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    記述言語:日本語   出版者・発行元:日本航空宇宙学会  

  • 極超音速機表面での放電による空力モーメント制御に関する研究

    渡邉 保真, 鈴木 宏二郎

    宇宙科学技術連合講演会講演集   59   6p   2015年10月 (   ISSN:1884-1945 )

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    記述言語:日本語   出版者・発行元:日本航空宇宙学会  

  • 東京大学柏キャンパス極超音速高エンタルピー風洞 招待 査読

    鈴木宏二郎, 今村 宰, 内海正文, 岡本光司, 奥抜竹雄, 津江光洋, 寺本 進, 中谷辰爾, 山口和夫, 渡邉保真

    日本航空宇宙学会誌   63 ( 7 )   223 - 229   2015年7月 (   ISSN:0021-4663 )

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    記述言語:日本語   掲載種別:記事・総説・解説・論説等(学術雑誌)   出版者・発行元:一般社団法人 日本航空宇宙学会  

    東京大学柏キャンパスに設置されている極超音速高エンタルピー風洞について紹介する.1つの空気加熱器に対し,極超音速風洞と燃焼風洞の測定部を有する1加熱器2運転モードを採用していることが最大の特徴である.設備概要と性能,気流特性に加え,1)広範囲での融合的研究の場とするため実験は公募制とし,外部ユーザーも積極的に受け入れること,2)大学設備としての安全性と低コスト性,高運転頻度を実現すること,3)大学の研究室として持続的に管理ができること,を旗印にした運用についても説明する.設備情報や行われてきた実験プロジェクト内容はホームページで公開されており,外部ユーザーの便宜が図られている.さらに,極超音速・高温気流実験装置の利用範囲を広げていくためのきっかけとなるものと期待して,分野融合的な実験例も紹介する.

    DOI: 10.14822/kjsass.63.7_223

  • 渦流れとその崩壊の数値解析における格子分解能の影響

    山田 健翔, 渡邉 保真, 鈴木 宏二郎

    年会講演会講演集   46   7p   2015年4月

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    記述言語:日本語   出版者・発行元:日本航空宇宙学会  

  • 多方向差分法を用いた乱流の直接数値シミュレーション

    山田 暁, 渡邉 保真, 鈴木 宏二郎

    年会講演会講演集   46   10p   2015年4月

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    記述言語:日本語   出版者・発行元:日本航空宇宙学会  

  • 極超音速流中の半球澱み点付近における放電及び磁場による気流制御に関する基礎研究

    渡邉 保真, 鈴木 宏二郎

    年会講演会講演集   46   5p   2015年4月

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    記述言語:日本語   出版者・発行元:日本航空宇宙学会  

  • Aerodynamic control effect of surface DC plasma discharge at Mach-7 hypersonic flow

    Yasumasa Watanabe, Kojiro Suzuki

    46th AIAA Plasmadynamics and Lasers Conference   2015年

     詳細

    © 2015, American Institute of Aeronautics and Astronautics Inc, AIAA. All Rights Reserved. Flow control method using direct current (DC) plasma discharge in Mach-7 hypersonic flow was investigated as a method to improve aerodynamic characteristics of hypersonic vehicles. In this work, the effect of DC arc plasma discharge was investigated to clarify its flow control effectiveness both with numerical analysis and with hypersonic wind tunnel experiments. When a plasma discharge is maintained ahead of double-wedge shaped surface that represents a body flap of hypersonic vehicles, numerical simulation based on simple energy addition model that represent plasma was conducted and it revealed that the aerodynamic force acting on the slope significantly decreases by more than 10 percent. Experimental results also suggested that the force acting on the slope decreases a lot within a very short time less than 0.1 seconds, suggesting that the present plasma discharge configuration can serve as an efficient aerodynamic control technique with a very short response time.

    DOI: 10.2514/6.2015-2342

  • Study of bow-shock instability in front of hemispherical shell at hypersonic mach number 7

    Ashish Vashishtha, Yasumasa Watanabe, Kojiro Suzuki

    45th AIAA Fluid Dynamics Conference   2015年

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    © 2015, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved. In this study, the formation of bow-shock and its instabilities have been studied in front of axisymmetric blunt nose shapes, at hypersonic Mach number 7 to understand the physics of bow-shock instabilities. The three geometries have been investigated as concave hemispherical shell (with negative curvature), convex hemispherical shell (with positive curvature) and circular at plate (with zero curvature), with same characteristic diameter. The lift and drag force measurements and unsteady pressure measurements were performed for all three geometries. The bow-shock visualizations have been carried out by Schlieren system, using high-speed camera at 10000 fps in hypersonic wind tunnel. By using image processing method, bow-shock unsteadiness has been analyzed for all three geometries. The large deformations in bow-shock in front of hemispherical concave shell have been analyzed with unsteady pressure measurement and shock displacements at the center and the edges of the geometries. It is observed that the large bow-shock deformations for convex, at and concave shaped blunt nose sustain within time order of 0.1 ms, 0.5 ms and 100 ms to 200 ms, respectively.

  • RBCC搭載ブースター機の極超音速空力デザインに関する研究

    鈴木 宏二郎, 渡邉 保真, 船坂 百合香

    宇宙科学技術連合講演会講演集   58   6p   2014年11月 (   ISSN:1884-1945 )

     詳細

    記述言語:日本語   出版者・発行元:日本航空宇宙学会  

  • Study on nonequilibrium plasma discharge in hypersonic flow over flat plate

    Yasumasa Watanabe, Kojiro Suzuki

    51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 2013   2013年

     詳細

    Hypersonic flow control with plasma discharge has received a good deal of research attention in recent years. In this study, the direct current (DC) plasma discharge over a flat plate was investigated as a prospective futuristic aerodynamic control device. Spectroscopic analysis showed that the vibrational temperature of nitrogen molecule is 7000 K and the translational temperature is 3500 K at maximum, which suggested that the plasma is at a vibrationally nonequilibrium state. Since electromagnetic forces for the futuristic aerodynamic control can mainly be imposed on ionized molecules, a numerical analysis was conducted based on Park's Two-temperature model and Gupta's 11-species model in order to estimate the distribution of high vibrational-temperature region. It was revealed that the concentration of high-vibrational temperature region exists in the boundary layer over flatplate surface, which is consistent with the experimental result of vibrationally exited nitrogen molecular distribution. © 2013 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.

  • Investigation of arc plasma discharge in hypersonic flow over compression and expansion corner

    Yasumasa Watanabe, Kojiro Suzuki

    44th AIAA Plasmadynamics and Lasers Conference   2013年

     詳細

    Flow control with plasma discharge is one of the promising techniques for the futuristic aerodynamic control methods. In the present work, a hypersonic flow control method which utilizes a direct-current (DC) arc plasma discharge is investigated as a fundamental study on such a new device. Hypersonic wind tunnel experiments were conducted to measure the effect of the discharge on Mach-7 flow over a compression and a expansion corner. The experimental results showed that, in the case of the expansion corner, a large pressure fall induced by the plasma discharge was observed. However, the change in the entire flow field such as shock wave formation was not clear. In the case of the compression corner, the boundary separation at the corner is enhanced and enlarged by the discharge, causing the pressure to change near the plasma area. Numerical analyses were conducted on both of these cases to understand the mechanisms of the observed phenomena. Park's two temperature model and Gupta's 11-species model were employed to describe the plasma flow. In order to simulate the effects of the plasma, a simple energy addition model is proposed, where the discharge effect is replaced by an energy addition to both the translational-rotational and the vibrational-electron-excitation energy modes. The numerical results based on the proposed model successfully showed a good qualitative agreement with the experimental results for the nitrogen molecular light emission. It was revealed that the present idea of utilizing the DC arc discharge as a flow control method is more effective in manipulating the flow when it is applied to a compression corner.

    DOI: 10.2514/6.2013-3130

  • Study on chemical factory in hypersonic wind tunnel flow using ablation and electric discharge

    Kojiro Suzuki, Yasumasa Watanabe

    44th AIAA Thermophysics Conference   2013年

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    Chemical reactions in hypersonic flows have a potential to produce much more various species than those in a static chamber because of its nonequilibrium nature. In the present study, we propose a new experimental technique of a "chemical factory" in a hypersonic wind tunnel flow. The hypersonic chemical factory is composed of a model with ablative part as a materials supplier, a pair of electrodes for electric discharge as an energy supplier, and a wake flow behind the body in frozen chemistry as a products transporter. To demonstrate this concept and to experimentally simulate the formation of prebiotic materials in high temperature shock layer around an ablating icy object entering the early earth's CO2/N2 atmosphere, a model with an ablative nose part made from water ice and dry ice is tested in the hypersonic wind tunnel at Mach number 7 in Kashiwa campus, the University of Tokyo. When the plasma discharge is ignited between the electrodes located on the side surface of the model, we observed the emission probably from CN species produced from the N element in the air and the C element in the ablation gas. The presence of CN suggests the production of HCN, which is one of the most important prebiotic materials, in hypersonic flows around extraterrestrial icy entry objects on the early earth. On the other hand, no signal of CN is observed in case of the nose made from water ice only. To assist the design of the experimental setup and to deepen our understanding on the phenomena, the thermochemical nonequilibrium Navier-Stokes analysis with C-H-O-N 28 species is also conducted. The results show reasonable agreement with the experimental observation. The present technique of the hypersonic chemical factory seems promising for investigation on nonequilibrium chemical process in a flow.

  • Effect of impulsive plasma discharge in hypersonic boundary layer over flat plate

    Yasumasa Watanabe, Kojiro Suzuki

    42nd AIAA Plasmadynamics and Lasers Conference   2011年

     詳細

    担当区分:筆頭著者, 責任著者  

    The application of plasma discharge to hypersonic flow control methods has received a good deal of research attention in recent years. As a fundamental study for such methods, direct current plasma discharge in Mach-7 hypersonic flow over flat plate was investigated both with wind tunnel experiments and numerical analyses. Impulsive discharge in a boundary layer over flat plate caused a decrease in the wall pressure around electrodes. For the purpose of clarifying the principal cause of this phenomenon, a numerical analysis was conducted by solving the three-dimensional Navier-Stokes equations with impulsive energy addition to the flow. Numerical results revealed that the pressure oscillates in the vicinity of heated region, which suggests that the fluctuation of surface pressure observed in the experiment could be qualitatively explained as the unsteady response of the flow to the impulsive Joule heating by the discharge. © 2011 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.

    DOI: 10.2514/6.2011-3736

  • Effects of plasma discharge on hypersonic flow over flat plate

    Yasumasa Watanabe, Osamu Imamura, Kojiro Suzuki

    41st AIAA Plasmadynamics and Lasers Conference   2010年

     詳細

    As a preliminary study on the application of plasma discharge to hypersonic aerodynamic control, the effect of direct current (DC) plasma in a hypersonic flow was examined with wind tunnel experiments. It was shown that the pressure rises significantly in the upstream region of the discharge. To the contrary, the pressure decreases in the region very close to the electrodes. This pressure change would be applied to a new aerodynamic control device. Under the assumption that the effects of the plasma discharge in a hypersonic flow are mainly due to the Joule heating, three-dimensional Navier-Stokes analyses were conducted. It was concluded that the pressure change far from the plasma area can be explained as an effect of the heat addition to the flow. © 2010 by the American Institute of Aeronautics and Astronautics, Inc.

▼全件表示

講演・口頭発表等

  • 超小型衛星技術と将来型大気突入技術について 招待

    渡邉保真

    第1回 非晶質材料に関する研究会;医療から宇宙まで  ( 愛知県名古屋市 )   2024年3月 

     詳細

    会議種別:口頭発表(招待・特別)  

  • 航空宇宙分野における機械工学 招待

    渡邉保真

    豊田工業高等専門学校,機械工学特論  ( 愛知県豊田市 )   2023年12月 

     詳細

    会議種別:口頭発表(招待・特別)  

  • 3Uサイズ小型火星探査機におけるエアロシェルを利用した大気突入時空力特性

    渡邉保真, 真鍋 慧大

    令和5年度宇宙航行の力学シンポジウム  ( 神奈川県相模原市,JAXA宇宙科学研究所 )   2023年12月 

     詳細

    会議種別:口頭発表(一般)  

  • Fundamental study on plasma-assisted flow control at external nozzle of high-speed transport vehicle 国際会議

    Yasumasa Watanabe

    76th Annual Meeting of the American Physical Society Division of Fluid Dynamics, APS DFD2023  ( Washington D.C., The United States )   2023年11月 

     詳細

    会議種別:口頭発表(一般)  

  • Numerical Investigation of Viscous Effects on Centreline Shock Reflection in Supersonic Ring Intakes 国際会議

    H. Ogawa, M. Matsunaga, A. Shibakita, C. Fujio, J. K. J. Hew, R. W. Boswell, S. Mölder, B. Shoesmith, R. Tahir, E. Timofeev, Y. Higa, Y. Watanabe, T. Handa, K. Ohtani

    Twentieth International Conference on Flow Dynamics  ( Sendai Miyazaki )   2023年11月 

     詳細

    会議種別:口頭発表(一般)  

  • 放電プラズマを利用した燃料点火とそれによる高速気流制御に関する基礎研究

    渡邉保真

    第67回宇宙科学技術連合講演会  ( 富山県富山市 )   2023年10月 

     詳細

    会議種別:口頭発表(一般)  

  • 極超音速気流中及び機壁表面で水の相変化に関する基礎研究

    渡邉保真

    第67回宇宙科学技術連合講演会  ( 富山県富山市 )   2023年10月 

     詳細

    会議種別:口頭発表(一般)  

  • Performance Test and Estimation of Orbital Control Authority of Micro Water Resistojet Thruster for Small Satellites 国際会議

    Kaname Yokota, Yasumasa Watanabe

    34th International Symposium on Space Technology and Science, 12th Nano- Satellite Symposium  ( Kurume Fukuoka )   2023年6月 

     詳細

    会議種別:口頭発表(一般)  

  • Fundamental Aerodynamic Study on Small Atmospheric Entry Probes for Multi-point Mars Exploration 国際会議

    Keita Manabe, Yasumasa Watanabe

    34th International Symposium on Space Technology and Science, 12th Nano- Satellite Symposium  ( Kurume Fukuoka )   2023年6月 

     詳細

    会議種別:口頭発表(一般)  

  • Study on water-ice behavior and subsequent water-flow interaction in Mach-7 hypersonic flow 国際会議

    Yasumasa Watanabe

    34th International Symposium on Space Technology and Science, 12th Nano- Satellite Symposium  ( Kurume Fukuoka )   2023年6月 

     詳細

    会議種別:口頭発表(一般)  

  • 超音速流制御に適用可能な超音波駆動型シンセティックジェットの開発

    湯浦聡史、渡邉保真、古谷克司、半田太郎

    2022年度衝撃波シンポジウム  ( 茨城県つくば市 )   2023年3月 

     詳細

    会議種別:口頭発表(一般)  

  • 航空宇宙分野における機械工学 招待

    渡邉 保真

    豊田工業高等専門学校,機械工学特論  ( 豊田工業高等専門学校(愛知県豊田市) )   2023年2月  豊田工業高等専門学校

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    会議種別:口頭発表(招待・特別)  

  • 陽極酸化型感圧塗料を用いた柱状構造による窓及び建造物壁面での衝撃波強度低減に関する研究

    田島つぶら*, 渡邉 保真, 小谷明*, 半田 太郎

    第18回 学際領域における分子イメージングフォーラム  ( 調布航空宇宙センター )   2022年12月  宇宙航空研究開発機構(JAXA)

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    会議種別:口頭発表(一般)  

  • FLEET光を利用した超音速流れの密度計測法に関する研究 国際会議

    山口和伽子*, 渡邉 保真, 杉岡洋介 JAXA**, 小池俊輔 JAXA**, 半田 太郎

    第18回 学際領域における分子イメージングフォーラム  ( JAXA )   2022年12月 

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    会議種別:口頭発表(一般)  

  • Characterisation of Centreline Reflection for Inward-Turning Axisymmetric Shock Waves 国際会議

    Hideki Ogawa Kyushu University**, Masanobu Matsunaga Kyushu University**, Justin Kin Jun Hew Australian National University**, Roderick W. Boswell Australian National University**, Chihiro Fujio Kyushu University**, Yoshitaka Higa*, Yasumasa Watanabe, Taro Handa, Kiyonobu Ohtani Tohoku University**

    19th International Conference on Flow Dynamics  ( Sendai )   2022年11月 

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    会議種別:口頭発表(一般)  

  • Study on Visualization Method for Axisymmetric Shock Reflection in Supersonic Flow 国際会議

    Yoshitaka Higa TTI*, Yasumasa Watanabe, Taro Handa, Masanori Matsunaga Kyushu University**, Chihiro Fujio Kyushu University**, Hideaki Ogawa Kyushu University**, Kiyonobu Ohtani Tohoku University**

    19th International Conference on Flow Dynamics  ( Sendai )   2022年11月 

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    会議種別:口頭発表(一般)  

  • Effect of Angle of Attack on Bow Shock Instabilities in frontal hemispherical cavity at Hypersonic Flow 国際会議

    Ashish Vashishtha **, Yasumasa Watanabe, Kojiro Suzuki **

    ESA Workshop: Aerothermodynamics and Design for Demise(ATD3 workshop) 2022  ( フランス,ボルドー )   2022年10月  欧州宇宙機関

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    会議種別:口頭発表(一般)  

  • 放電を利用した火星飛行機のスケールに関する考察

    渡邉 保真

    第60回飛行機シンポジウム  ( 新潟県新潟市 )   2022年10月  日本航空宇宙学会

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    会議種別:口頭発表(一般)  

  • 超音速流中における軸対称衝撃波反射の可視化手法に関する研究 国際会議

    比嘉良貴 豊田工大*, 渡邉 保真, 半田 太郎, 松長真宣 九大**, 藤尾秩寛 九大**, 小川秀朗 九大**, 大谷清伸 東北大**

    第54回流体力学講演会/第40回航空宇宙数値シミュレーション技術シンポジウム  ( 岩手 )   2022年7月  日本航空宇宙学会

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    会議種別:口頭発表(一般)  

  • 空気吸い込み式プラズマジェット噴射による極超音速空力特性制御に関する基礎研究 Fundamental Study on Hypersonic Aerodynamic Characteristics Control using Air-breathing Plasma Jet Blowing

    下永 祥史 **, 渡邉 保真, 鈴木 宏二郎 **

    第54回流体力学講演会/第40回航空宇宙数値シミュレーション技術シンポジウム  ( 岩手県盛岡市 )   2022年6月  日本航空宇宙学会

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    会議種別:口頭発表(一般)  

  • 極超音速流中の楔型モデルから発生する衝撃波による近傍場圧力測定

    丸宮 知季 **, 渡邉 保真, 鈴木 宏二郎 **

    第54回流体力学講演会/第40回航空宇宙数値シミュレーション技術シンポジウム  ( 岩手県盛岡市 )   2022年6月  日本航空宇宙学会

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    会議種別:口頭発表(一般)  

  • 高周波フラッピング噴流による斜め衝撃波/境界層干渉流れの能動制御に関 する研究 国際会議

    湯浦聡史(豊田工大)*, 青木塁(豊田工大)*, 渡邉 保真, 半田 太郎

    第54回流体力学講演会/第40回航空宇宙数値シミュレーション技術シンポジウム  ( 岩手県盛岡市 )   2022年6月  日本航空宇宙学会

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    会議種別:口頭発表(一般)  

  • 小型ロケット機体回収のための極超音速ロガロ翼に関する基礎研究

    太田 和志 **, 渡邉 保真, 鈴木 宏二郎 **

    第54回流体力学講演会/第40回航空宇宙数値シミュレーション技術シンポジウム  ( 岩手県盛岡市 )   2022年6月  日本航空宇宙学会

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    会議種別:口頭発表(一般)  

  • マッハ5極超音速風洞の製作・放電気流制御と着氷研究

    渡邉 保真

    令和4年度極超音速統合制御実験(HIMICO)研究会  ( オンライン )   2022年6月  JAXA

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    会議種別:口頭発表(一般)  

  • DEVELOPMENT AND FLIGHT PLAN OF NANOSATELLITE BEAK FOR BREAKTHROUGH TECHNOLOGY DEMONSTRATION USING DEPLOYABLE AEROSHELL 国際会議

    Yasunori Nagata et al. (13th out of 14 authors)*, Yasumasa Watanabe

    2nd International Conference on Flight Vehicles, Aerothermodynamics and Re-entry Missions Engineering, FAR 2022  ( ドイツ,ハイルブロン )   2022年6月  欧州宇宙機関

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    会議種別:口頭発表(一般)  

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受賞

  • 宇宙賞

    2018年3月   日本機械学会宇宙工学部門   展開型エアロシェル実験超小型衛星(EGG) チーム

    鈴木宏二郎, 今村宰, 山田和彦, EGG開発チーム

  • 若手奨励賞優秀論文賞

    2016年1月   日本航空宇宙学会 第59回宇宙科学技術連合講演会  

    渡邉保真

  • 学生賞

    2009年2月   日本航空宇宙学会  

    渡邉保真

科学研究費補助金

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奨学寄付金・研究助成金 ※本学入職以降の業績のみ

  • イオン伝導性ガラスを用いた超小型人工衛星に搭載可能なタンクレス固体推進機の開発

    公益財団法人豊田理化学研究所 2024年4月 - 2025年3月

    渡邉 保真

  • 放電プラズマを利用した極超音速気流制御と燃焼を利用した能動的空力制御への応用

    公益財団法人豊田理化学研究所 2023年4月 - 2024年3月

    渡邉 保真